Alstom Technology Limited

Alstom

Alstom (switzerland) Ltd

Ansaldo Energia Switzerland Ag

Alexander Ni

Richard Carroni

Franz Joos

Wolfgang Polifke

Sasha Savic

Peter Jansohn

Bruno Schuermans

Peter Flohr

Majed Toqan

Gianfranco Ludovico Guidati

Ken-Yves Haffner

Valter Bellucci

A method is provided for separating COfrom an exhaust gas flow of a combustion process. The method includes: compressing the gas flow and cooling the compressed gas flow. The method also includes feeding the cooled gas flow to a swirl nozzle and separating the COfrom the gas flow in the swirl nozzle. The method also includes discharging the COwhich is separated in the swirl nozzle from the swirl nozzle for separate further treatment. A COseparating device is also provided that separates COfrom an exhaust gas flow of a combustion process that operates with fossil fuels. The device includes a swirl nozzle which is exposed to through-flow of the gas flow, a compressor located upstream or downstream of the swirl nozzle, and a plurality of cooling devices which are provided upstream of the swirl nozzle for cooling of the gas flow which comes from the compressor.

[object Object]

A combustion chamber (), in particular in a gas turbine, has at least two burners (A-H) that are connected to a fuel supply () via controllable fuel valves (' and). Each burner (A to H) is assigned at least one optical measuring device () for detecting chemiluminescent radiation, and the combustion chamber () is assigned a pressure sensor () for detecting a combustion chamber pressure. The optical measuring device () and the pressure sensor () are connected to a computing and control device, which calculates a correlation value from the incoming measured values. A high correlation value signifies that the associated burner is prone to pulsation. The computing and control device () is designed in such a way that it determines the burner or a burner group with the highest correlation and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group, and the pulsation tendency thereof is thereby reduced.

Combustion chamber

In an atomizer device for the production of a liquid-gas mixture (), the mixture () is introduced, particularly for compression, into a nozzle arrangement () in which the kinetic energy of the mixture () is in large part converted into compression energy by a pressure rise of the air. The atomizer device () includes a central air feed () and a nozzle chamber () for the supply of liquid surrounding the air feed. At or in the atomizing device, means () are arranged in the nozzle chamber for producing a swirled liquid flow in the nozzle chamber (), and the swirled liquid flow emerges via a nozzle aperture () surrounding the air feed.

Atomizer device and method for the production of a liquid-gas mixture

In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first () and one second compressor (), a combustion chamber (), and a turbine (). At least one intermediate cooler () is located between the first () and second compressor (). The intermediate cooling takes place at least in part or for the most part isentropically.

Method for intermediate cooling and gas turbine system with intermediate cooling

In a combustion device ( ), particularly for driving gas turbines, comprising a plurality of burners ( ) of identical thermal power output, which work parallel to an axis ( ) into a common combustion chamber ( ), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners ( ) are designed differently from one another in such a way that the flames ( ) or flame fronts generated by them are positioned so as to be distributed along the axis ( ).

Combustion device for generating hot gases

In a combustion apparatus ( ), in particular for driving gas turbines, in which combustion apparatus ( ) a gaseous fuel in a burner ( ) is sprayed through a plurality of separate fuel-injection devices ( ) into a gas flow containing combustion air, and the resulting mixture flows into a combustion chamber ( ) for combustion and burns there, the acoustic impedance or stiffness of the fuel-injection devices ( ) is selected to be different in order to avoid thermoacoustic combustion instabilities.

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Baden, Switzerland

Alexander Ni